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FedEx > 767 Systems (ASM 8) > Flashcards

767 Systems (ASM 8) Flashcards

1
Q

Overhead Panel Organization (gen)

A

H: Hydraulics
E: Electrics
F: Fuel
A: Air

Flight Controls
Landing Gear & Breaks

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2
Q

ACFT Electrical System Components (elec)

A
  1. Main AC Power (main source of ACFT power)
  2. Main DC Power
  3. Battery / STBY Power
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3
Q

AC Electrical Power Sources (elec)

A
  1. LT & RT Engine IDG’s
  2. APU Gen
  3. External Power
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4
Q

AC Busses (elec)

A
  1. LT/RT Main AC Busses
  2. LT/RT AC Transfer Busses
  3. CA/FO Flight Instrument Transfer Busses
  4. LT/RT Utility Busses
  5. Galley Bus
  6. Ground Service Bus
  7. Ground Handling Bus
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5
Q

Autoland Power Source (elec)

A
  1. Left AP and CA Flight Instrument Transfer Bus: LT Main AC System
  2. Right AP and FO Flight Instrument Transfer Bus: RT Main AC System
  3. Center AP: Batt/STBY System

Autoland: 3 independent power sources via 3 isolated busses to 3 different autopilots

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6
Q

Autoland Loss of Generator Above 200’ (elec)

A

NO LAND 3

Both Tie breakers close, remaining GEN powers both LT and RT AC bussed
LT Main System power the Center Autopilot

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7
Q

Autoland Loss of Generator Below 200’ (elec)

A

Autoland continues using remaining 2 autopilots

Both Bus Tie breakers remain open
Autopilot who’s Gen failed, remains unpowered
Flight instruments powered through the FLT Inst Transfer Busses

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8
Q

DC Electrical Power Source (elec)

A
  1. LT/RT Main AC Busses (through TRU’s to produce DC)

* No flight deck controls for Main AC System*

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9
Q

DC Busses (elec)

A
  1. LT/RT Main DC Busses
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10
Q

Batt/STBY Power Sources (elec)

A

No Power to ACFT: Source is Battery

Power to ACFT: Source is Batt Charger or LT Main DC (through Main AC)

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11
Q

Batt/STBY Busses (elec)

A
  1. Hot Batt Bus
  2. Batt Bus
  3. STBY AC Bus
  4. STBY DC Bus
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12
Q

HDG (elec)

A

Hydraulic Driven Generator

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13
Q

HDG (elec)

When Activated:
Power Source:
Provides Power To:

A

When Activated: Automatically when loss of both LT and RT Main AC Busses

Power Source: Center Hydraulic System

Provides Power To: 
AC
1. LT AC Transfer Bus
2. RT AC Transfer Bus
3. STBY AC Bus
4. CA Flight Inst Transfer Bus

DC

  1. Hot Batt Bus
  2. Batt Bus
  3. STBY DC Bus
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14
Q

Number of Fuel Tanks and Qty (fuel)

A

3 tanks

  1. LT Main / 6,000 gal / 40,000 lbs
  2. RT Main / 6,000 gal / 40,000 lbs
  3. Center / 12,000 gal / 80,000 lbs

Total 24,000 gal / 160,000 lbs

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15
Q

Fuel Low Level Warning (fuel)

A

LT or RT Main Tank below 2,200 lbs

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16
Q

Where is fuel temp taken (fuel)

A

RT Main Tank

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17
Q

of Fuel Pumps (fuel)

A

2 in each tank

A single pump can supply one engine

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18
Q

Fuel Pumps Power Source (fuel)

A

All 6: AC Power

DC fuel pump for APU if no AC Power (1 located in the left main)

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19
Q

What tanks drain first (fuel)

A

Center - center pumps have greater output

Center pumps automatically power off when tank is dry

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20
Q

How does the APU get its fuel (fuel)

A

Any AC fuel pump - supply’s to left fuel manifold

DC - fuel pump in the LT Main Tank

  * no controls or indications
  * Auto Ops when no AC power*
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21
Q

FUEL CONFIG light (fuel)

A
  1. Imbalance, 2000 between LT and RT Main tanks
  2. Center fuel pump switched off with more than 1200 lbs in tank
  3. LOW FUEL displayed on EICAS, LT or RT Main tank < 2200 lbs
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22
Q

How to fix a fuel imbalance (fuel)

A
  1. Open X-Feed

2. Turn OFF fuel pumps in tank with the lowest qty

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23
Q

Fuel Jettison (fuel)

Tank:
Pump:
Rate:

A

Tank: Center Fuel Tank
Pump: 2 fuel pumps
Rate: 2600 lbs/min

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24
Q

How to turn on Fuel Jettison (fuel)

A

FUEL JETTISON selector ON
jettison transfer valves open
jettison Pumps operate

FUEL JETTISON NOZZLE switches ON
nozzle valves open

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25
Q

How is fuel calculated during dump (fuel)

A

Durning Dump
FMC discontinues calculations
Totalizer valve is used

After Dump
Calculated value will reset using totalizer value

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26
Q

Totalizer vs Calculated Fuel (Fuel)

A

Totalizer: Measurement of each tank

Calculated: Measurement of START fuel - FUEL USED

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27
Q

Nitrogen Generator System NGS (fuel)

A

Converts bleed air to nitrogen enriched air to prevent a dry center fuel tank from having explosive gasses

No flight crew action

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28
Q

Suction Fuel Feed (fuel)

A

Each engine can get fuel from its corresponding Main Tank

GND: Ok
Climb: dissolved air in the tank could cause a flame-out
Cruise: may be able to (after dissolved air depletes)

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29
Q

How many Hydraulic Systems (HYD)

A

3 systems

  1. Left
  2. Center
  3. Right
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30
Q

What does hydraulics power (HYD)

A
  1. Flight Controls
  2. Flaps/Slats
  3. Gear
  4. Brakes
  5. Nose Wheel Steering
  6. Tail Skid
  7. Autopilot Servos
  8. Yaw Damper
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31
Q

Left Hydraulic System (HYD)

Powers
Source

A

Powers

  1. Flight Controls
  2. Right Yaw Damper
  3. Stab Trim module
  4. Trapped fluid used by PES

Source

  1. Engine-Driven Primary Pump
  2. Electrical-Driven Primary Pump
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32
Q

Right Hydraulic System (HYD)

Powers
Source

A

Powers

  1. Flight Controls
  2. Normal Brakes
  3. Pitch Enhancement System (PES)

Source

  1. Engine-Driven Primary Pumps
  2. Electrical-Drive Primary Pumps
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33
Q

Center Hydraulic System (HYD)

Powers

A
  1. Flight Controls
  2. Flaps/Slats
  3. Gear
  4. Alternate Brakes
  5. Nose Wheel Steering
  6. Tail Skid
  7. Left Yaw Damper
  8. HDG - Hydraulic Driven Generator
  9. Stab Trim module
  10. Reserve fluid used by C1 for reserve brakes and steering.
34
Q

Center Hydraulic System (HYD)

Source

A

Reservoir

  1. 2 Electrical-Driven Primary Pumps
  2. Air-Driven Demand Pump
  3. RAT (for flight controls)
35
Q

Center System Hydraulic Leak, What Remains (HYD)

A

Reservoir maintains reserve fluid for

  1. Brakes
  2. Steering

Reserve Brakes and Steering isolation
Center #1 electric-driven primary pump is auto isolated if low qty

36
Q

HDG (HYD)

A

Hydraulic Driven Generator - Provides AC Power

HDG is automatically powered by “C” Hyd System when both Main AC busses are lost

37
Q

RAT (HYD)

A

Ram Air Turbine - Provides HYD Power

RAT provides hyd power to flight controls portion of the Center Hyd System

Adequate HYD power at speed above 130 kts
In flight, auto deploys when both engines fail
Manually deploys by pressing button

38
Q

Hydraulic Fluid Symbols (HYD)

RF
OF
QTY

A 
RF = Re-Fill
OF = Over Filled
QTY = Quantity is Low
39
Q

Speed Brake Lever (flt cont)

Positions and Ops

A

Down:
All spoilers retract

ARMED:
After landing, lever moves up and spoiler panels extend

UP:
Spoiler panels expanded max (flight or ground)

On the ground:
Trust Lever advanced to T/O position - Lever moves DOWN
Either Thrust Reverser raised to reverse idle - Lever moves UP
lever does not need to be armed

40
Q

SPEED BRAKE light (flt cont)

A

If the speed brakes are extended and,

  1. RA is 800’ or below
  2. Flaps in the landing position
41
Q

Flap Lever (flt cont)

Position and Ops

A

UP:
Slats and Flaps are retracted

1:
Slats - Extend (midrange)
Flaps - Retracted

5, 15, 20:
Slats - Extended (remain midrange)
Flaps - Commanded Position

25, 30:
Slats - Fully Extended
Flaps- Commanded Position

42
Q

T/O and Landing Flaps setting (flt cont)

A

T/O: 5, 15, 20
Landing: 25, 30

Flaps 1 = Slats Extend

43
Q

Flaps gate (flt cont)

A

1 - Prevents inadvertent retraction of the Slats

20- Prevents inadvertent retractions of the flaps past Go-Around position

44
Q

Primary and Secondary Flight Controls (flt cont)

A

Primary:

  1. Elevator
  2. Ailerons
  3. Rudder

Secondary:

  1. Horizontal Stab
  2. Spoilers
  3. Slats
  4. Flaps
45
Q

Flight Controls Powered by (flt cont)

A

Elevator - HYD L/C/R
Rudder - HYD L/C/R
Spoilers - HYD L/C/R

Ailerons - HYD L/R

Stab - HYD L/C (it is a mixed combination)

Flaps/Slats - HYD C (Alternate is through electric motors)

46
Q

Flight Controls for Pitch (flt cont)

A

2 Elevators

Horizontal Stab

47
Q

Flight Controls for Roll (flt cont)

A

4 Ailerons

12 Spoilers

48
Q

Flight Controls for Yaw (flt cont)

A

Single Rudder

49
Q

Stab Trim Control source (flt cont)

A
  1. Electric (yoke)
  2. Alternate (pedestal)
  3. Automatic (autopilot)
50
Q

Pitch backup (flt cont)

A

Pitch Enhancement System - PES

Hydraulic motor in the RIGHT system drives a pump that uses fluid from the LEFT trim system to operate the Stab

  • Auto activation if both L/C Hyd System lost in flight*
  • Only electric trim is available*
51
Q

Control Jam (flt cont)

A

Pitch: Significant force fwd/aft causes columns to OVRD STAB
Roll: Significant force L/R causes columns to OVRD

52
Q

Flaps Load Relief (flt cont)

A

Flaps 25 or 30 speed exceeded, flaps automatically revert to 20

as you slow down, they re-extend

53
Q

Alternate Flaps (flt cont)

A

Manually operates through electric motors

  • max flaps 20 (due to FDX Ops because no asym protection)*
  • ** No Flaps asymmetry protection / time increases***
54
Q

Degrees of Steering (gear)

A

Tiller: 65°
Pedals: 7°

Tiller overrides pedals

55
Q

Air / Ground Sensing (gear)

A

Tilt sensor on Main Gear

Strut compression sensor on Nose Gear

56
Q

How is the gear held up (gear)

A

Main: Door structure
Nose: Up locks

57
Q

Power source for gear retraction (gear)

A

Center HYD System

58
Q

Power source for gear extension (gear)

A

Primary: Center HYD System

Alternate: Electric motor trim locking mechanism
Free-fall to the down and locked position

59
Q

Power source for Nose Wheel Steering (gear)

A

Primary: Center HYD System

Alternate: Reserve Brakes and Steering System
Provides hyd fluid to the Center #1 electric primary hyd pump, this pump pressure is exclusive to the alternate Brakes and NWS system

60
Q

Brake System Components (gear)

A
  1. Normal Brakes - HYD System “R”
  2. Alternate Brake - HYD System “C” (automatic if “R” system lost / if fluid lost to “C” system, trapped fluid and #1 elec pump provides Reserve Brakes and Sterling)
  3. Brake Accumulator
  4. Anti-Skid Protection
  5. Auto Brake System
  6. Parking Brake
61
Q

Power Source for Brakes (gear)

A
  1. Normal Brakes: Right HYD System
  2. Alternate Brakes: Automatic - Center HYD System (automatic)
  3. Reserve Brakes and Steering: Push switch - Provides HYD fluid to center #1 Electric Primary HYD Pump
  4. Brake Accumulator: If Normal and Alt brakes lost, Accumulators provide several brake applications or parking brake
62
Q

Power source for Anti-Skid Protection (gear)

A
  1. Normal Brakes HYD System

2. Alternate Brakes HYD System

63
Q

Power source for Auto Brakes System (gear)

A
  1. Normal Brake HYD System - ONLY
64
Q

Auto Brakes RTO (gear)

A

Max Brake pressure if,

  1. ACFT is on the ground
  2. Ground speed is above 85 knots
  3. Both Thrust Levers are retarded to idle
65
Q

Auto Brakes on Landing (gear)

A
  1. Both Thrust Levers idle
  2. The wheels have spun up
  • 5 levels of deceleration - rotary selector
  • On dry RWY, manual brakes are stronger
  • Provides braking to full stop or disarmed
66
Q

Auto Brakes Disarm (gear)

A
  1. Pedal brakes applied
  2. Either Thrust Reverser advanced after landing
  3. Speed Brake Lever move from full UP position
  4. DISARM or OFF selected on Auto Brake selector
  5. Auto Brake fault
  6. Normal anti-skid fault
67
Q

Power source Parking Brake (gear)

A
  1. Normal Brakes HYD System
  2. Alternate Brake HYD System
  3. Brake Accumulators - Right HYD System (brake press indicator left side)
68
Q

Power source Tail Skid (gear)

A

Uses Main Landing Gear Actuation System

70
Q

LDS

A

Large Display System

15” LCD’s

71
Q

IRS

A

Inertial Reference System

72
Q

ISSP

A

Instrument Source Select Panel

73
Q

MCP

A

Mode Control Panel

74
Q

PFD/ND

A

Primary Flight Display Nav Display

75
Q

ISFD

A

Integrated Standby Flight Display

76
Q

SEI

A

Standby Engine Indictor

77
Q

EICAS

A

Engine Indication and Crew Alert System

78
Q

TMSP

A

Thrust Mode Select Panel

79
Q

ASA

A

Autoland Status Annunciator

80
Q

MCDU

A

Multi-Function Control Display Unit

81
Q

EFIS-DCP

A

Electronic Flight Instrument - Display Control Panel

82
Q

ACP

A

Audio Control Panel

FedEx (20 decks)

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